국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	LOADING TESTS OF A WING STRUCTURE FOR A HYPERSONIC AIRCRAFT
저자	R. A. Fields, L. F. Reardon and W. H. Siegel
Keyword	Hypersonic aircraft; Load tests; Spot welds; Stress-strain diagrams; Wing panels.
URL	http://www.dfrc.nasa.gov/DTRS/1980/PDF/H-1046.pdf
보고서번호	NASA-TP-1596
발행년도	1980
출처	NASA Dryden Flight Research Center
ABSTRACT	Room-temperature loading tests were conducted on a wing structure designed with a beaded panel concept for a Mach 8 hypersonic research airplane. Strain, stress, and deflection data were compared with the results of three finite-element structural analysis computer programs and with design data. The test program data were used to evaluate the structural concept and the methods of analysis used in the design. A force stiffness technique was utilized in conjunction with load conditions which produced various combinations of panel shear and compression loading to determine the failure envelope of the buckling critical beaded panels The force-stiffness data did not result in any predictions of buckling failure. It was, therefore, concluded that the panels were conservatively designed as a result of design constraints and assumptions of panel eccentricities. The analysis programs calculated strains and stresses competently. Comparisons between calculated and measured structural deflections showed good agreement. The test program offered a positive demonstration of the beaded panel concept subjected to room-temperature load conditions.